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Acta Astronautica
IF
2.48
Papers
10161
Papers 10107
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Published on Jul 1, 2019in Acta Astronautica 2.48
Thomas Riel1
Estimated H-index: 1
(TU Wien: Vienna University of Technology),
Andreas Sinn1
Estimated H-index: 1
(TU Wien: Vienna University of Technology)
+ 2 AuthorsGeorg Schitter27
Estimated H-index: 27
(TU Wien: Vienna University of Technology)
Abstract This paper investigates the tracking accuracy of an optical telescope system used for satellite tracking and laser ranging applications. The investigated system uses a high precision motion controller and a pointing model based on spherical harmonics to achieve high accuracy. To overcome the limitations due to local pointing model inaccuracies and dynamic effects during tracking, an iterative trajectory learning algorithm is proposed. The implementation, as well as the stability analysi...
Published on Jul 1, 2019in Acta Astronautica 2.48
Ye Hong (TUM: Technische Universität München), Zhanyi Liu + 3 AuthorsZhendong Yu (TUM: Technische Universität München)
Abstract Given growing competition in the business space launch market, more researchers are evaluating the merit of methane as a potential propellant. In this study, a rocket combustion chamber with a single coaxial shear injector is tested. Gaseous oxygen and gaseous methane are employed in the hot firing tests at 2 MPa and a mass ratio of oxidizer to fuel of 2.65. Along the chamber axis, the wall temperatures are recorded; an inverse heat conduction approach forms the basis of the wall heat f...
Published on Jul 1, 2019in Acta Astronautica 2.48
Robert-Jan Koopmans1
Estimated H-index: 1
,
Varun Nandyala + 7 AuthorsCarsten Scharlemann7
Estimated H-index: 7
(University of Applied Sciences Wiener Neustadt)
Abstract A new technology for the manufacturing of 3D-printed ceramic catalyst support structures enables further optimisation of the catalyst, including the size and the internal geometry. An important design consideration for catalysts used in monopropellant thrusters is the size for a given design thrust level. A too small size may lead to only a partly decomposition of the incoming propellant. A too large size may lead to unnecessary heat loss to the environment and an excessive pressure dro...
Published on Nov 1, 2019in Acta Astronautica 2.48
Haoyang Peng2
Estimated H-index: 2
(National University of Defense Technology),
Weidong Liu9
Estimated H-index: 9
(National University of Defense Technology)
+ 2 AuthorsWei-Yong Zhou
Abstract Methane-air Continuous Rotating Detonation (CRD) has been firstly achieved in this paper in the hollow chamber with a Laval nozzle, and the diameter of the chamber is just 100 mm. The contraction ratio of the Laval nozzle is a key factor for the CRD realization. CRD can only be obtained when the contraction ratio is no less than 4, but its ER operating range decreases in the increase of contraction ratio from 4 to 10. For all the success cases, the average propagation frequency and velo...
Published on Jul 1, 2019in Acta Astronautica 2.48
Alexandra Wander1
Estimated H-index: 1
,
Konstantinos Konstantinidis2
Estimated H-index: 2
+ 1 AuthorsPhilipp Voigt (EADS: Airbus)
Abstract The growing population of space debris is posing a threat to future spacecraft in Earth orbit. The technology for self-removal of spacecraft, TeSeR, is an innovative project of eleven European partners coordinated by Airbus Defense & Space within the HORIZON2020 framework of the European Union with the goal to develop a removal module that can be carried into orbit by future spacecraft of any size and mass into any orbit, interconnected only by a standardized interface. At early 2019, a...
Published in Acta Astronautica 2.48
Shuji Yang (NUAA: Nanjing University of Aeronautics and Astronautics), Hao Wen11
Estimated H-index: 11
(NUAA: Nanjing University of Aeronautics and Astronautics),
Dongping Jin11
Estimated H-index: 11
(NUAA: Nanjing University of Aeronautics and Astronautics)
Abstract This paper presents a trajectory planning method for a dual-arm space robot that is free-floating and receives no actuation from the base spacecraft. The task is to capture a target by a mission arm and accomplish base manoeuvring with the coupling effects by a manoeuvring arm. Three manoeuvring cases for the base are discussed concerning attitude regulation, attitude tracking and position tracking. In all cases, an optimization method is applied to solve for the joint velocity of the a...
Published on Jul 1, 2019in Acta Astronautica 2.48
Qimeng Xia (BIT: Beijing Institute of Technology), Ningfei Wang9
Estimated H-index: 9
(BIT: Beijing Institute of Technology)
+ 4 AuthorsLiang Ren
Abstract The vacuum arc thruster (VAT) is considered to be a potential micro-thruster because of its simple structure and high specific impulse. The plume downstream from the cathode spot region of a co-axial type thruster with external magnetic field is analyzed by numerical simulation. Plasma velocity, temperature and density are used to represent the influence of the cathode spot region. When the magnetic field is applied, the plume is significantly affected even at the intensity of 0.03 T. M...
Published on Nov 1, 2019in Acta Astronautica 2.48
Abstract Simulator sickness is a common problem when using centrifuge-based flight simulator. During centrifuge-based training, achieving a G-baseline level and returning to a complete stop after each G-profile still cause unpleasant sensations and motion sickness. The aim of this study was to determine the optimal G-baseline level and the optimal approach motion cueing when the centrifuge-based flight simulator achieved and returned from this G-baseline level. A model of motion sickness inciden...
Published on Jul 1, 2019in Acta Astronautica 2.48
Xianlei Cheng2
Estimated H-index: 2
(National University of Defense Technology),
Peng Wang3
Estimated H-index: 3
(National University of Defense Technology)
+ 2 AuthorsGuojian Tang10
Estimated H-index: 10
(National University of Defense Technology)
Abstract This paper proposes an effective control scheme to address the robust tracking control problem of the flexible air-breathing hypersonic vehicle subject to actuator dynamics. The whole vehicle dynamics is decomposed into the velocity subsystem and altitude subsystem, and the nonlinear disturbance observer based dynamic surface control is employed in the controller design within both subsystems. In order to tackle the input constraints, different hyperbolic tangent functions are carefully...
Published on Nov 1, 2019in Acta Astronautica 2.48
Siebo Reershemius1
Estimated H-index: 1
(DLR: German Aerospace Center),
Mark Fittock2
Estimated H-index: 2
(DLR: German Aerospace Center)
+ 5 AuthorsTorben Wippermann2
Estimated H-index: 2
(DLR: German Aerospace Center)
Abstract On May 05, 2018 NASA JPL launched its mission to Mars called “InSight”. Main objective of this mission is to gain more knowledge of the evolution of terrestrial planets. Beside a number of different scientific instruments onboard the lander there are two instruments that will perform measurements on the Martian ground. One of the instruments is HP 3 (Heat Flow and Physical Properties Package), which was developed by the German Aerospace Center (DLR) to measure the heat flow of the Marti...
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